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Latest Publications
FinSim Rocket Equation Burnout Velocity
Accuracy Compared to
Finite Difference and TR-10 Prediction, viXra
e-print archive (2022)
Ring Fin Rocket Center of
Pressure, Drag and Lift Slope Coefficients
Measured
Using the AeroRocket Wind Tunnel,
Technical Note
2022-2
(2022)
Spool Rocket Center of
Pressure and Drag Coefficient Measured
Using the AeroRocket Wind Tunnel,
Technical Note
2022-1
(2022)
Warp Drive
Propulsion Using Magnetic Fields to
Distort Space-Time OR
First
Successful Warp Drive Flight
(2021)
POF 291 Flutter Velocity Error Produces Negative Margins of
Safety Compared to NACA TN 4197,
Technical Note
2021-2
(2021)
FinSim 10 Torsional Stiffness of Rocket Fins
Thickness-Tapered From Root to Tip,
Technical Note 2021-1
(2021)
"Proving Shock Thickness Decreases for
Increasing Mach Number", Shock Wave
Thickness Analysis (2020)
"Demonstrating the Relationship
Between
Quantum Mechanics and Relativity",
Theory of Everything (2019)
Experimental Rocket
Launches
Micro-vehicles
Launched on Jets of High
Velocity Water
HTV-3X Space Plane Development
Sprint Experimental Rocket
Sprint Model Rocket
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AeroRocket
specializes in subsonic,
supersonic and hypersonic aerodynamics, Computational Fluid Dynamics
(CFD), warp drive physics and aerospace related
software development for rockets, airplanes and gliders. Other services include wind tunnel testing using
the AeroRocket designed and fabricated subsonic
wind tunnel and supersonic
blow-down wind tunnels.
AeroCFD®
is a registered trademark of John Cipolla and is
classified as an axisymmetric 3-D and planar 2-D
Computational Fluid Dynamics (CFD) computer program.
However, AeroCFD solutions are not limited to bodies of
revolution even though AeroCFD's bodies of revolution
can be very complex.
John Cipolla
Chief Aerodynamicist,
AeroRocket and WarpMetrics
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Nozzle 10:
One-dimensional and two-dimensional,
compressible flow computer program for the analysis of
converging-diverging nozzles, including ramjet and scramjet engines. Nozzle models inviscid, adiabatic and hence isentropic flow of a
calorically perfect gas through variable-area ducts. Nozzle internal flow may be entirely subsonic, entirely
supersonic or a combination of subsonic and supersonic including
shock waves in the diverging part of the nozzle. Shock waves are
clearly identified as vertical red lines on all plots.
 The cross-sectional
shape in the axial direction of the nozzle is specified by selecting
from five standard nozzle types or by defining nozzle geometry
using the Free-Form nozzle geometry method. Nozzle plots color
contours of pressure ratio, temperature ratio, density ratio,
and Mach number and has a slider bar that displays real-time values
of all nozzle flow properties. New in this version is the ability
to determine shock-angle, jet-angle (plume-angle) and Mach number
for axisymmetric and two-dimensional nozzles in the region near
the lip for underexpanded and overexpanded flow. The converging-diverging nozzle
featured in the new AeroRocket supersonic blow-down wind tunnel
was designed
using
Nozzle
applying the concept of a normal shock diffuser.
More ...
HyperCFD
10:
Supersonic and
hypersonic re-entry vehicle and rocket analysis computer program
based on advanced principals of 3-D Gasdynamics. HyperCFD,
determines
drag coefficient
(Cd), center of pressure (Xcp), CN-alpha and Cm-alpha of supersonic
and hypersonic rockets and re-entry vehicles. In addition, on
a separate screen HyperCFD displays and plots CN-Body, CN-Fins,
CN-Total and
 Cm-Total as a function of angle of attack (AOA)
using up/down controls. HyperCFD uses empirical aerodynamic corrections to
the modified Newtonian surface inclination method that allows
excellent results from Mach 1.05 to Mach 20. Includes a wide
variety of nose cone shapes and fin cross-sections. Nose cone
shapes include, conical, elliptical, parabolic, power series
Sears-Haack, tangent ogive and spherical segment. Fin
cross-sections include single wedge, symmetrical double wedge,
arbitrary double wedge, biconvex section, streamline section,
round-nose section, and elliptical section fin shapes. HyperCFD is useful to
determine supersonic and hypersonic rocket drag and center of
pressure location for medium and large scale professional sounding
rockets. Finally,
HyperCFD 10.xx models hypersonic glide vehicle (HGV)
aerodynamics.
More ...
FinSim 10, Flutter
Velocity Tool: Quickly and easily
predict fin flutter velocity, UF and fin divergence velocity, UD for any rocket while
specifying fins in the Fin Geometry screen by simply using a slider bar. Predict flutter velocity from
sea level all the way to maximum altitude that was defined on the main AeroFinSim
analysis screen. Get instant flutter velocity feedback while specifying fin
geometry and get an idea of fin shock angle and fin Surface Mach number that a fin will
experience during supersonic flight. Flutter velocity accuracy is enhanced by using the
NASA web site atmospheric model that
predicts free stream pressure (P) temperature (T), density (r)and speed of sound as a
function of altitude from sea level while flying through the Troposphere
(h < 36,152 feet),
Lower Stratosphere (36,152 feet < h < 82,345 feet) and finally the Upper Stratosphere
(h > 82,345 feet). The atmospheric
model used in FinSim is not limited to only the Troposphere or 36,152 feet.
More ...
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